Defense Intelligence Reference Document Laser Lightcraft Nanosatellites

Defense Intelligence Agency · 77 pages · text from the file's own layer

This Defense Intelligence Reference Document from the Defense Intelligence Agency, dated 1 November 2010, was produced under the Advanced Aerospace Weapon System Applications (AAWSA) Program. It describes nanosatellite technologies and proposes launching nanosats into orbit with laser Lightcraft propulsion. It also covers a weapon mission selection study and multi-megawatt laser options. The author recommends that the Department of Defense and NASA bring Lightcraft R&D back to the United States and restart the X-50LR flight demonstration program.

Open the PDF at page 71 Original source ↗

“Masse”33 pages

p. 4 …Influence of Target Velocity and Intercept Angle on Impact Energy and Required Mass .................................................................................................. 33 Table 5…
p. 5 …The term "minisatellite" refers to a spacecraft with a wet mass (including onboard propellant) of 100…
p. 7 …Nanosatellite Technologies OVERVIEW Nanosats require technologies that radically reduce the mass and power of components without…
p. 8 …nanosat presents some unique challenges, with low mass (0.25 kg) and low power (0.5…
p. 9 …In order to develop a low mass C&DH, a lightweight and low power electronics packaging…
p. 11 …RF COMMUNICATIONS The onboard RF subsystem must be small, low mass, and low power. The system…
p. 12 …additional strain on an already challenged nanosat mass and power budget. For this reason, the concept…
p. 13 …The material will be selected based on mass, cost, manufacturability, ease of assembly and integration, and…
p. 15 …for the spacecraft because a large propellant mass and heavy energy source are not carried onboard…
p. 17 …Current Lightcraft designs are limited to about 60 g mass and 15 cm in diameter by…
p. 21 …It requires a beam power of 0.1 to 1 MW per kg of vehicle mass…
p. 22 …The majority of the system mass required to launch a payload to orbit is left on…
p. 24 …Therefore, this would allow approximately 4 kg of mass to be placed into orbit with the…
p. 25 …same ply-thickness) to meet Lightcraft airframe mass requirements. Another important finding in the study was…
p. 31 …Additional estimated mass for performing the Lightsat function is no more than about 1 kg, if…
p. 32 …Lightcraft takeoff masses no more than about 20 kg can be accelerated to orbital velocities by…
p. 33 …for missile and maneuvering aircraft interception. • Additional mass along Lightcraft centerline for hardened target penetration. LIGHTCRAFT…
p. 34 …Lightcraft sizing assumed a propellant mass fraction of 0.5 and 1.0 MW of laser…
p. 35 …Hybrid Rocket Expendible Launch Vehicle - Assumed Perfonnance and Estimated Weights Payload Mass (kg) 1.00 5…
p. 37 …It is therefore estimated that the air-to-space Lightcraft dry mass would be about the…
p. 38 …Influence of Target Velocity and Intercept Angle on Impact Energy and Required Mass 2 61. Lightcraft…
p. 39 …Influence of Lightcraft and Target Velocity on Impact Energy and Required Mass 261. Lightcraft Lightcraft Impact…
p. 40 …The lower mass also saves launch costs, so the total system costs less for the same…
p. 41 …many spacecraft that the economics of true mass production will come into play in space for…
p. 44 …the local vertical, with its center of mass in GEO. The Fresnel zone plate has a…
p. 46 …wall plug and optical efficiencies, cost, complexity, mass, and size. Free-electron lasers are another class…
p. 47 …P = 2000 Pa (or 0.02 atmospheres). • Mass flow rate, Q = 60 kg/sec per module…
p. 48 UNCLASSIFIED//509 AEEJCJOP 11£5 O.-blf + Total mass flow rate, Qtota1 = 240 kg/sec for…
p. 50 …sec, and 15 kg/sec of CD2 mass flow represents 2.053 x 1026 molecules/sec…
p. 51 …The 60 kg/sec mass flow requirement of the 3: 1 N2/C02 lasing gases means…
p. 53 …mass (not including the prime power and cooling systems) to achieve the low specific mass (5…
p. 65 …is the undulator period, mis the electron mass, and c is the speed of light. 'MeV…
p. 72 …The Lightcraft specific impulse is essentially infinite (several thousand seconds in rocket mode), while payload mass…

UNCLASSIFIED/ ,'f81l 8ffl@lit.la tl91!! 9Hl:Y
I
Mitigating the Atmosphere with
Adaptive Optics
• Beacon
00
.~
~• The AO System needs to operate (sense, compute, and ad1ust the deformable
I mirror} approx.> 10X faster than the atmosphere changes (-10's -100's hz}
Figure 36. HEL Adaptive Optics System (courtesy of the Directed Energy Professional
Society).
All of these HEL beam control innovations can be quickly adapted to laser propulsion
applications with little or no additional technical modifications or R&DTE. It is expected
that all of the R&DTE work presently being done by the various DoD directed energy
weapons/HEL programs can be immediately leveraged for laser Lightcraft nano-/pico-
satellite programs should they become established. Primary mirrors with exit apertures
of~ 10 m will be required to launch laser-propelled Lightcraft from ground/sea to LEO
while apertures on aircraft-mounted laser beam control optics will be~ 1.0 m.
67
UNCLASSIFIED/ )F8A 8FFI&I.«1k Wfi&i a••k>/

Not linked to a story yet.

About this file

Report, from the dia collection. The PDF is mirrored here; the original link is under it. 77 pages are in the text index: search them above, or from the library's search.